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Application number
GB3860565A
Inventor
Edward Fischel
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Individual
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Individual
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Publication of GB1216072ApublicationCriticalpatent/GB1216072A/en
G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
G01C21/16—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
G01C21/18—Stabilised platforms, e.g. by gyroscope
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Engineering & Computer Science
(AREA)
Radar, Positioning & Navigation
(AREA)
Remote Sensing
(AREA)
Automation & Control Theory
(AREA)
Physics & Mathematics
(AREA)
General Physics & Mathematics
(AREA)
Vibration Prevention Devices
(AREA)
Gyroscopes
(AREA)
Abstract
1,216,072. Gyroscopic apparatus. E. FISCHEL. Sept. 9, 1965 [Sept. 23, 1964], No.38605/65. Heading G1C. A gimbal mounted gyro stabilized platform is characterized in that the platform and the gimbals are mounted in a closed platform casing filled with a liquid, the specific weight of which is equal to the resulting specific weight of the platform and the individual gimbals. By this means, gimbals, platform and liquid are moved as an integral and, when mounted in an aircraft or rocket, no deforming forces due to accelerations become effective on the gimbals, which forces could give rise to resonance oscillations of the gimbals. Thus only the ordinary aircraft or rocket vibrations without resonance amplification become effective on the gyros.
Frequency model for the GI-T 1-B single degree of freedom rate integrating gyroscope(Development of frequency model for single degree of freedom rate integrating gyroscope using Eulerian formulation)
Stability analysis of an unstable ballistic missile with attitude and rate gyros providing the stabilizing feed back signals, using the direct method of lyapunov
Employment of asymptotic methods in solving problems about the movement of an astatic gyroscope in cardan suspension(Asymptotic method for solution of system of two nonlinear differential equations)
Analysis of guidance system errors resulting from initial misalignments of both the accelerometer and stabilizing gyros, the drift of the stabilized element during flight and errors in measuring the vehicle motions
Stability of the stabilized platform of an inertial navigation system with friction in the accelerometers(Equations for instability of stabilized platform of inertial navigation system with viscous friction in accelerometers)
Systematic departures of the triaxial gyroscopic platform, caused by its angular oscillations(Approximation method and motion equations for determining systematic drifting of triaxial stabilized platform due to angular oscillations)
Propagation of the 26-month fluctuations in the stratosphere at extraequatorial latitudes(Propagation of 26-month oscillations in meridional component of wind velocity in stratosphere at extraequatorial latitudes from hydrothermodynamic equations solution)